CN109404060B - Variable geometry mixed flow turbocharger sealing structure - Google Patents
Variable geometry mixed flow turbocharger sealing structure Download PDFInfo
- Publication number
- CN109404060B CN109404060B CN201811501683.3A CN201811501683A CN109404060B CN 109404060 B CN109404060 B CN 109404060B CN 201811501683 A CN201811501683 A CN 201811501683A CN 109404060 B CN109404060 B CN 109404060B
- Authority
- CN
- China
- Prior art keywords
- bearing shell
- large end
- diffuser
- hole
- small end
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000007789 sealing Methods 0.000 title claims abstract description 25
- 238000009413 insulation Methods 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims description 5
- 239000007789 gas Substances 0.000 description 36
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 230000008021 deposition Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention provides a sealing structure of a variable geometry mixed flow turbocharger, which comprises a bearing shell, a nozzle blade shaft, a diffuser and a heat insulation wall, wherein the heat insulation wall is fixed at the small end of the bearing shell; u-shaped ring grooves are respectively processed at the large end and the small end of the bearing shell, and a one-way valve body is arranged in the U-shaped ring groove at the large end of the bearing shell; a gas channel for communicating the one-way valve body with a U-shaped ring groove at the small end of the bearing shell is processed on the bearing shell; the diffuser is arranged at the large end of the bearing shell, a large end ring cavity is formed by the diffuser and a U-shaped ring groove at the large end of the bearing shell, a small end ring cavity is formed by the small end of the bearing shell and the heat insulation wall, an air hole which is opposite to the large end ring cavity is formed in the diffuser, compressed air enters the large end ring cavity through the air hole, and the pressure difference is utilized to open the one-way valve body to enter the small end ring cavity through the air channel. The invention can effectively reduce the exhaust gas leakage of the variable geometry turbocharger.
Description
Technical Field
The invention belongs to the technical field of turbochargers of internal combustion engines, and particularly relates to a sealing structure of a variable geometry mixed flow turbocharger.
Background
An exhaust gas turbocharger is one of the key core kits for achieving high power density, low fuel consumption and low emission for diesel engines. In order to adapt to different requirements of different working conditions of the engine on the supercharger, the low working condition performance of the diesel engine is optimized, the fuel economy of the diesel engine is improved, and the application of the variable geometry turbocharger is a trend of the technical development of the supercharger. However, as the working condition of the diesel engine changes, a gap exists between the nozzle vane shaft and the bearing housing, and in the operation process of the variable geometry turbocharger, the diesel engine cabin is polluted due to the fact that fuel gas is easily leaked from the gap position, carbon is deposited at the gap position when the variable geometry turbocharger is operated for a long time, and the reliable operation of the nozzle vane shaft is affected.
Therefore, in order to reduce the exhaust gas leakage of the variable geometry mixed flow turbocharger and ensure the reliable operation of the variable geometry turbocharger, it is critical to design an efficient variable geometry turbocharger sealing structure to solve the above problems.
Disclosure of Invention
In view of the above, it is an object of the present invention to provide a variable geometry mixed flow turbocharger sealing structure to solve the problem of poor sealing between the nozzle vane shaft and the bearing housing.
The invention provides a sealing structure of a variable geometry mixed flow turbocharger, which comprises a bearing shell, a nozzle blade shaft, a diffuser and a heat insulation wall, wherein the heat insulation wall is fixed at the small end of the bearing shell, a yielding hole is formed in the heat insulation wall, a shaft mounting hole is formed in the small end of the bearing shell, the nozzle blade shaft is arranged on the shaft mounting hole, one end of the nozzle blade shaft penetrates through the yielding hole, and the nozzle blade shaft is in clearance fit with the shaft mounting hole; u-shaped ring grooves are respectively processed at the large end and the small end of the bearing shell, two valve mounting holes are processed at symmetrical positions of the U-shaped ring grooves at the large end of the bearing shell, and one-way valve bodies are respectively mounted in the two valve mounting holes and fixed by snap rings; a gas channel for communicating the valve mounting hole with the U-shaped ring groove at the small end of the bearing shell is processed on the bearing shell, and a sealing screw plug for sealing the gas channel is arranged in a process hole of the gas channel; the diffuser is arranged on the end face of the large end of the bearing shell, a large end ring cavity is formed by the diffuser and the U-shaped ring groove of the large end of the bearing shell, a small end ring cavity is formed by the small end of the bearing shell and the heat insulation wall, an air hole opposite to the large end ring cavity is formed in the diffuser, compressed gas at the compressor end enters the large end ring cavity through the air hole, and the one-way valve body is opened by utilizing pressure difference to enter the small end ring cavity through the gas channel.
In addition, it is preferable that two piston rings with buckles are installed in the piston ring groove of the nozzle vane shaft, the buckles are staggered by 180 degrees, and simultaneously, the outer circumferential surface of the piston ring is contacted with the inner wall surface of the yielding hole to form a sealing structure.
Further, it is preferable that the flow area of the gas hole is larger than the area of the gas passage.
Compared with the prior art, when the variable geometry mixed flow turbocharger sealing structure provided by the invention works, compressed gas at the compressor end enters the small end ring cavity of the bearing shell to prevent the exhaust gas at the vortex end from entering, so that the exhaust gas leakage of the turbocharger is effectively reduced; the sealing structure can also reduce carbon deposition at the positions of the nozzle vane shaft and the bearing shell mounting holes, reduce the probability of locking of the nozzle vane shaft, and simultaneously, the compressed gas can cool the nozzle vane shaft, so that the running reliability of the variable geometry turbocharger is improved; the sealing structure utilizes the gas channel of the bearing shell of the supercharger, does not need an external pipeline, and has ingenious structural design and convenient installation.
Drawings
Other objects and results of the present invention will become more apparent and readily appreciated by reference to the following description and claims in conjunction with the accompanying drawings and a more complete understanding of the invention. In the drawings:
FIG. 1 is a schematic structural view of a variable geometry mixed flow turbocharger seal according to an embodiment of the invention;
FIG. 2 is a schematic structural view of a variable geometry mixed flow turbocharger bearing housing according to an embodiment of the invention;
FIG. 3 is an enlarged view of a portion of FIG. 1 at A;
fig. 4 is a partial enlarged view at B in fig. 1.
Wherein reference numerals include: the gas compressor comprises a compressor shell 1, a bearing shell 2, a large end 21, a small end 22, a gas inlet shell 3, a diffuser 4, a one-way valve body 5, a sealing screw plug 6, a nozzle vane shaft 7, a piston ring 8, a heat insulation wall 9 and a gas channel 10.
The same reference numerals will be used throughout the drawings to refer to similar or corresponding features or functions.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1 to 4, the variable geometry mixed flow turbocharger seal structure of the embodiment of the invention includes: bearing shell 2, the diffuser 4, nozzle vane axle 7 and thermal-insulated wall 9, bearing shell 2 is located between compressor shell 1 and the gas shell 3 that admits air, bearing shell 2 includes big end 21 and tip 22, big end 21 is close to compressor shell 1, tip 22 is close to gas shell 3 that admits air, the terminal surface at big end 21 is fixed to diffuser 4, thermal-insulated wall 9 is fixed at tip 22, the hole of stepping down has been seted up on thermal-insulated wall 9, the axle mounting hole has been seted up at tip 22, nozzle vane axle 7 is installed on the axle mounting hole and one end passes thermal-insulated wall 9's hole of stepping down, nozzle vane axle 7 and axle mounting hole clearance fit, nozzle vane axle 7 rotates with the axle mounting hole as the center, in the in-process of nozzle vane axle 7 rotation contact with the inner wall of hole of stepping down all the time.
U-shaped ring grooves are respectively processed at the large end 21 and the small end 22, two valve mounting holes are processed at symmetrical positions of the U-shaped ring grooves at the large end 21, one-way valve bodies 5 are respectively arranged in the two valve mounting holes, and the one-way valve bodies 5 are fixed in the valve mounting holes through snap rings; a gas channel 10 is processed on the bearing shell 2, the gas channel 10 is used for communicating a valve mounting hole and a U-shaped annular groove of the small end 22, a sealing screw plug 6 for sealing the gas channel 10 is arranged in a process hole of the gas channel 10, and the gas channel 10 is sealed by the sealing screw plug 6.
In order to bleed air from the diffuser 4, air holes are formed in the diffuser 4, the flow area of the air holes is larger than the area of the gas channel 10, the diffuser 4 and the U-shaped annular groove of the large end 21 form a large end ring cavity, the small end 22 and the heat insulation wall 9 form a small end ring cavity, the positions of the air holes are opposite to the large end ring cavity, compressed gas at the compressor end enters the large end ring cavity through the air holes, and the check valve body 5 is opened through pressure difference to enter the small end ring cavity through the gas channel 10. When the small end ring cavity is filled with compressed gas, the pressure in the small end ring cavity is higher than the pressure of exhaust gas in the vortex end gas channel, so that the compressed gas in the small end ring cavity can prevent the exhaust gas from entering the vortex end ring cavity by a sealing structure formed by the nozzle blade shaft 7 and the yielding holes of the heat insulation wall 9, the leakage amount of the exhaust gas at the vortex end is effectively reduced, and a large amount of exhaust gas is prevented from leaking.
In order to better prevent exhaust gas leakage, two piston rings 8 with buckles are arranged in piston ring grooves of the nozzle vane shaft 7, the two buckles are staggered by 180 degrees, and meanwhile, the outer circumferential surfaces of the piston rings 8 are in contact with the inner wall surfaces of the yielding holes to form a fit, so that the yielding holes of the nozzle vane shaft 7 and the heat insulation wall 9 form a sealing structure, exhaust gas at the turbine end is prevented from leaking from a gap between the nozzle vane shaft 7 and a shaft mounting hole of the bearing shell 2, carbon deposition at the positions of the nozzle vane shaft 7 and the shaft mounting hole can be reduced by the sealing structure, and the probability of blocking of the nozzle vane shaft 7 is reduced.
The foregoing is merely illustrative embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about variations or substitutions within the technical scope of the present invention, and the invention should be covered. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (3)
1. The utility model provides a variable geometry mixed flow turbocharger seal structure which is characterized in that, including bearing shell, nozzle blade axle, diffuser and thermal-insulated wall, wherein, the thermal-insulated wall is fixed in the tip of bearing shell, the thermal-insulated wall has seted up the hole of stepping down, the tip of bearing shell has seted up the axle mounting hole, nozzle blade axle is installed on the axle mounting hole and one end pass the hole of stepping down, nozzle blade axle is clearance fit with the axle mounting hole;
u-shaped ring grooves are respectively processed at the large end and the small end of the bearing shell, two valve mounting holes are processed at symmetrical positions of the U-shaped ring grooves at the large end of the bearing shell, and one-way valve bodies are respectively mounted in the two valve mounting holes and fixed by snap rings; a gas channel for communicating the valve mounting hole with the U-shaped ring groove at the small end of the bearing shell is processed on the bearing shell, and a sealing screw plug for sealing the gas channel is arranged in a process hole of the gas channel;
the diffuser is arranged on the end face of the large end of the bearing shell, a large end ring cavity is formed by the diffuser and the U-shaped ring groove of the large end of the bearing shell, a small end of the bearing shell and the heat insulation wall form a small end ring cavity, an air hole, the position of which is opposite to the large end ring cavity, is formed in the diffuser, compressed air at the compressor end enters the large end ring cavity through the air hole, and the one-way valve body is opened through pressure difference and enters the small end ring cavity through the air channel.
2. The variable geometry mixed flow turbocharger sealing structure according to claim 1, wherein two piston rings with buckles are installed in the piston ring groove of the nozzle vane shaft, the buckles are staggered by 180 degrees, and simultaneously, the outer circumferential surface of the piston rings is contacted with the inner wall surface of the relief hole to form a sealing structure.
3. The variable geometry mixed flow turbocharger seal according to claim 1, wherein a flow area of the air hole is larger than an area of the gas passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811501683.3A CN109404060B (en) | 2018-12-10 | 2018-12-10 | Variable geometry mixed flow turbocharger sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811501683.3A CN109404060B (en) | 2018-12-10 | 2018-12-10 | Variable geometry mixed flow turbocharger sealing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109404060A CN109404060A (en) | 2019-03-01 |
| CN109404060B true CN109404060B (en) | 2024-02-02 |
Family
ID=65458126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811501683.3A Active CN109404060B (en) | 2018-12-10 | 2018-12-10 | Variable geometry mixed flow turbocharger sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109404060B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110671165B (en) * | 2019-11-13 | 2024-08-20 | 重庆江增船舶重工有限公司 | Expansion power generation integrated high-speed expander |
| CN111663965B (en) * | 2020-07-23 | 2024-09-13 | 重庆江增船舶重工有限公司 | Mixed-flow turbocharger vortex end sealing structure for sequential supercharging mode |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB642585A (en) * | 1945-06-02 | 1950-09-06 | Lockheed Aircraft Corp | Improvements in or relating to an internal combustion turbine power plant |
| CN201627605U (en) * | 2010-01-21 | 2010-11-10 | 重庆德蚨乐机械制造有限公司 | Sealing and heat insulation structure at vortex end of turbocharger |
| CN209129685U (en) * | 2018-12-10 | 2019-07-19 | 重庆江增船舶重工有限公司 | Variable-geometry mixed-flow turbocharger sealing structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0710911D0 (en) * | 2007-06-07 | 2007-07-18 | Cummins Turbo Tech Ltd | A turbocharger sealing arrangement |
| US8695337B2 (en) * | 2010-03-31 | 2014-04-15 | Cummins Turbo Technologies Limited | Gas sealing arrangement for a variable geometry turbocharger |
-
2018
- 2018-12-10 CN CN201811501683.3A patent/CN109404060B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB642585A (en) * | 1945-06-02 | 1950-09-06 | Lockheed Aircraft Corp | Improvements in or relating to an internal combustion turbine power plant |
| CN201627605U (en) * | 2010-01-21 | 2010-11-10 | 重庆德蚨乐机械制造有限公司 | Sealing and heat insulation structure at vortex end of turbocharger |
| CN209129685U (en) * | 2018-12-10 | 2019-07-19 | 重庆江增船舶重工有限公司 | Variable-geometry mixed-flow turbocharger sealing structure |
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| Publication number | Publication date |
|---|---|
| CN109404060A (en) | 2019-03-01 |
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